Vertical take-off high-speed aircraft



July 5, 1960 s. HILLER, JR

VERTICAL TAKE-OFF HIGH-SPEED AIRCRAFT Filed July 6, 1954 MiO .NkvR

INVENTOR. fM/vL/.fr ,ly/LER JR.

"A fron/viv;

July 5, 1960 s. HILLER, JR 2,943,816

VERTICAL TAKE-OFF HIGH-SPEED AIRCRAFT Filed July 6, 1954 3 Sheets-Sheet2 l' YJ JNVENTOR. .fm/wir ,6l/LER JR,

July 5, `1960 Filed July 6, 1954 S. HILLER, JR

VERTICAL TAKE-OF`F HIGH-SPEED AIRCRAFT 3 Sheets-Sheet 3 INVENTOR.

STANLEY //L/.ER JR,

WIMAM "ATTORNEYS 2,943,816 f'vjnR'rICAL TAKE-oFF HIGH-SPEED AIRCRAFIStanley IIiller,'.lr., Atherton, Calif., assignor to Hiller :AircraftCorporation, Palo Alto, Calif., a corporation 'ofV California*V v Filediluly 6, 1954, Ser. No. 441,353 1f4c1ims. (ci. 24a-2s) This inventionrelates to high-speed aircraft capable of vertical take-oli and landingoperations. f

It is an object of the invention to provide an aircraft powered by aturbine or pulse jet system, or the like, with a plurality of tail orthrust pipes rleading from the engine to suitably spaced points to servealso as landing gear for the ship and which is provided with means tocontrol the relative thrust from the engine through the individualthrust pipes to establish and control flight direction. A further objectof the invention is the provision in such an aircraft of means to varythe directionv of exhaust or thrust from the tail pipes to counteractany tendency of the craft to yaw or spin in flight. Another object ofthe invention is to provide such a craft of simple construction and witha single control member operable by a pilot to obtain desired quantityand direction controls overthe gases passing through the individual tailpipes and also to provide control of fuel feed to the engine.

The invention will best be understood by reading the followingdescription with reference to the accompanying drawings, wherein a smallor single occupant craft embodying the principles of the presentinvention is described and illustrated. I

InV the drawings: a v V Fig. l is va schematic view illustrating anaircraft em# bdying the present invention as it would appear in severalpositions during transition from a take-off positions through normaliflight, and return to a landing position; ..Fig.:12 isa View'l of thesame aircraft in side elevation `with some parts omitted, and some partsbroken'away to disclose portions of operating mechanism; Fig. 3 is anenlarged section of a portion of the operatngfmechanism taken onlineIII`'III of Fig. 2;

f `Eig'. 4is a plan View ofthe same craft with the pilot in positionthereon; and l Fig. 5 is an enlarged detail in section of a portion ofthe control mechanism;

-Referring first to Figs. l, 2, and 4, an aircraftconstruc-ted inaccordance with the present invention is illustratedI as having anengine housing Y designed to contain a turbine or pulse jet engine (notshown), and extending in an upright direction in the ground position ofthe ship. The. engine may be of any suitable conventional type. whichcauses forward motion of a craft by the thrust reaction of gases passingthrough a tail pipe, and the details of construction of the engineV arenot essential to an understanding of the presentV invention. Inaccordance with the present invention, the engine housing 10 isprovided'at its lower end with three jet thrust or tail pipesextendinginl an upright direction, and which receive substantially equalproportions of' gases discharged during the operation of the engine.These three pipes are substantiallyequally spaced apart in triangularformation to provide afforward pipe 11 and two rearwardly extendingpipes 12. The centers of the outlets of these pipesare preferablyequi-distant from the center of gravity-of the craft.v 'Ihe enginehousing andthe thrusty pipes are inter-b ,loe

connected and cooperate to provide the main body frame of the aircraftupon which the remaining aircraft structure is mounted. That is, thebody frame of the aircraft consists essentially `of two main portions,the engine housing and the thrust pipes which provide thelanding gearfor the aircraft.

A pair of stub wings or air foils, shown at 13, project outwardly fromopposite sides of the engine housing to facilitate stable flight. Apilots platform shown at 14 forms a connection between andserves as abrace forl the three thrust pipes. The pilot stands upon the platform 14in the position shown in Fig. l where he is directly behind a verticalpanel 15 which has a chest or torso pad 16 thereon, and is also providedwith a belt 17 to encircle the pilots waist. A hood or head protector 18is also preferably supported at the upper end of the r panel 1S and maybe made of any durable transparent material.

With a pilots station constructed in this manner, the pilot occupies astandingposition during vertical ascent and a forward reclining positionduring horizontal ilight with both hands always free to manipulate aliight control column, the construction and operation of which willpresently be described in detail. The pilot controls three essentialelements of ight of the craft which are thrust or speed, direction, andspin control or stability. All of these elements of flight arecontrollable through a single control column with a crossbar at itsupper end which is grasped in the pilots hands.

Thrust is controlled by the rate of fuel ow to the engine through athrottle valve. `Direction is controlled by dampers in the thrust pipesadapted to close or to partially close any of the pipes to increase therelative thrust from the others, and therefore vary the direction ofHight. Spin orryaw, which is the tendency of a craft to rotate about anaxis parallel to its direction of flight, is controlled, by flapsadjacent the ends of the thrust pipes which act somewhat in the mannerof flaps or ailerons on ordinary airfoils to vary the direction ofthrust reaction and thereby stabilize the craft in flight or overcomeits tendency to spin.A

The structure ofthe single control column its connections with theseveral controlled elements are sub- 'i ject to variation in design, butone practical form of this,V

Inechanisn'l is -illustrated in the drawings. Referring now to Fig. 2.,the control column is shown as comprising a short vertical post 20, thelower 'end of which is sup-V f ing a rearwardly inclined post 23 uponwhich is rotatably mounted a control member 24. The upper end of thecontrol member 24 carries a crossbar or handgrip 25 (see also Fig; 4)mounted on a suitable bearing for rocking motion about its ownhorizontal axis.

The supply of fuel to the engine is controlled by the handgrip 25, and,as shown in Fig. 2, fuel from a tank (not shown) in the stub wings 13'flows through a line 26 to a throttle valve 27, and thence through a`line 28 to the engine in housing 10. Throttle valve 27 may be opened orclosed by manipulation of a lever 259 disposed at its side; and thisylever is pivotally connected to' a link 30 connected to a pin 31 (seeFig. 3) secured to a cylindrical member 32 telescopically mounted in acylindrical base 33 suitably secured to pilots platform 14. A spring 3 4normally urges the cylindrical member 32 upwardly to eifect closing Vofthe throttle valve through link 3) and' lever 29; Stop members in theform of bolts, one of which is shown `at 35' in Fig. 3', limit rtheupward or closing movement of member 32;` 'g

i A cam plate 36's secured toethe top ofthe member 32Aand may bedepressed by a pair of pivoted cams 37 journalled on a cross member 38.A Bowden cable 39 or other suitable motion-transmitting mechanism, formsa connection between camsl and a, lever 40 xed to and projecting fromthe handgrip 25. Thus, upon rotaf tion of the handgrip 25 in a directionforwardly or -away from the pilot, cams 37 will be rockedto depress theelement 32 and open the throttle valve in the manner described.' The owof fuel to the enginewill preferably be underpressure.from-suitablepumping mechanism (notillustrated). n Mechanismforrcontrolli g direction of ilight is illustrated in Figs. 2, 4 -and 5,and comprises valvesor dampers 44.V One such damper is disposed intheforward thrust pipe 11 and in each of the two rearward thrust pipes 12.-Each damper is pivotally-mounted in its thrust pipe, and is capable ofrocking movementabout its pivotal support from a normal fully openedposition illustrated in Fig. 2 to a position at right angles theretowhere it will close the pipe to prevent the iiow of gases therethrough.Since the three thrust pipes are equally spaced about the center ofgravity of the craft, selective manipulationof the. dampers 44 isemployed to obtain directional control.. For example, by reference toFig. 1, a craft in vertical ascent will undergo transition to forwardight upon closing, or partially closing, the damper in the forwardthrust pipe 11. Then, when the craft is in forward or horizontal flight,transition to vertical flight willbe accomplished by closing, orpartially closing, the dampers in the rearward thrust pipes 12. In thesame manner, direction of flight 4in a horizontal plane may be varied bymanipulation of either one or the other of the dampers inthe rearwardthrust pipes 12. All three of the dampers44 are connected with thecontrol column by the mechanism shown in Figs. 2, 4 and 5.

Referring rst to Fig. 2, each damper is shown as having a lever 45 fixedto its pivotal support, and engaging a stop lug 46 which limits therocking movement of the damper in one direction to a full open position.Rocking of the lever 45. in the opposite direction tends to *close thedamper.. To accomplish closing movement, each lever 45 is pivotallyconnected to a rod'assembly including a rod 46 and whichis alsoVpivotally connected to a collar 47.secure d to the upperV end of theuniversally mounted post 20 of the control column. Each of rods 46' isspring pressed by a resilient assembly, shown in Fig. VV5,Vcomprisingra-springV Ahousing 48, into which the rod projects. .The endvof the rod in the spring housing carries a spring seat 49.slidable inIthe housing and adaptedtoV abut against xed seat 49' in the housing; aspring -50 being interposed between'seat 49 and an end closure member-51of the housing through which rod 46 is slidably mounted. The housing isitself directly connected to collar 47, as by anV eye bolt 52 and pinbolt 53. Y v

Spring 50 is under compression and normally thrusts rod 46 inwardly tohold the damper open against stop 46. When the control column isswungabout its universal support in the direction of any one damper, anoutward thrust is imposed upon the connecting rod 46 connected to suchdamper to swing lthe damper towards its closed position. However, due tothe resilient assemblies 48, the other two dampers remain fully open asthe rods 46 connected to such dampers are effectively lengthened bycompression of their associated springs 50. With the triangulararrangement shown, the control column when pulled rearwardly or towardthe pilot will tend to close both of the dampers in the thrust pipes 12.Similarly, direct forward motion of the control column closes the damperin the thrust pipe 11. It is also possible to impart closing movement tothe forward damper "asti-3,816 M as rolling or yawing, each of the threetail pipes is provided adjacent its end with a flap 55 normally disposedin a plane parallel to the ow of gas through the pipe. Swinging of theseflaps to either side causes impingement of the gases on that side with aresulting thrust reaction toward the opposite side to counteract anytendency of the craft to roll or yaw. Each flap 55 is pivotally mounted,and has a lever 56 fixed to its pivotal support and connected as by aBowden cable 57 or similar motion transmitting mechanism with thecontrol column. The connection of these cables with the control columnis shown in Fig. 2 as comprising a bracket 58 flxed to and extendingfrom the non-rotatable part 23 of the and one rear damper by a forwardoblique motion of the column. A lever 59 is pivotally mounted at theouter end of this bracket and all of the cables 57 are connected withthe lower end of this lever.

A connecting rod 60 extends between the upper end of theY lever 59 andapin 61Y supported in suitable brackets on one side of the rotatable part24 of the control column; rod 60 being universally connected to lever 59and pin 61. With this construction, rotation or twisting movement of thepart 24 about its own axis serves to rock the lever-,59 in eitherdirection. When the lever is rocked. clockwise, as viewed in Fig. 2, athrust will he imposed on the rear cables 57'to swing the flaps 55 inone direction andptensionis imposed on the forward cable 57 to swing theforward flap'SS in the same direction by virtue of the fact that thelever 56 on this ap is, as shown in Fig. 4, arranged in the oppositedirection looking outwardly from the vertical center line of the craft,with respect to the pivotal support of the ap. Consequently, by twistingthe control element 24 in opposite directions, all of the flaps 55 movetogether in either one direction or the other to create a thrustreaction for opposing the tendency of the craft to roll about its ownflight axis.

Supports or foot members shown at 65 (Figs. l and 4) may be xed to thelower or outer ends of the thrust pipes 11 and `12. to support them in aposition. slightly above the ground.

Fig. 1 of the drawings graphically depicts the manner of operation-ofthe craft as it progresses through vertical ascent, horizontal ight andvertical descent. Thespeed of vertical descent will of course becontrolled by manipulation of the throttle to the position wherethe'action of the gases emanating from the thrust or tail pipes nearlyoffsets the force of gravity upon the craft whereby the descent will beat'moderate speed and landing on these pipes which serve as the landinggear of the ship, will take place without excessive shock.

I claim: l

l. A jet propelled aircraft comprising an immovable housing for ajet-type engine, three thrust pipes leading from the housing to spacedexhaust points, dampers in the thrust pipes for varying the ow quantityof gases therethrough to control flight direction, an adjustable flapmovably mountedadjacent the end of each thrust pipe to insure stableflight, means to control llow of fuel to the engine, a pilot supportingplatform positioned between a pair of adjacent pipes and securedthereto, a, movable control column manually operable by a pilotsupported on said platform,rand connections between the control col-yumn and the dampers, aps and fuel control means to enable adjustmentthereof. v I Y 2. A jet propelled aircraft capableof vertical take offand landing comprising a main body frame consisting es-l sentially of ajet engine housing and a plurality of in-v dividual thrust pipes each ofwhich is immovably connected at one end to s aid housing and whichterminates at its other end at a point spaced from said housing, saidother ends of said pipes being cooperable to provide a support for theaircraft when the same isr at rest on the ground, said pipescommunicating with said housing whereby thrust reaction of. gasesproduced ina jet engine in, said housing'produces propulsion'of theaircraft,

'controlling saidyalve`v imeans.. l ealreraft.accordingito 2 with theaddition Vof'.fungus;adjacent said lower ends of said pipes. for des,

lectiugwgaseslilowing therefrom; to.,eifect spin control i of saidaircraft in ight.

4. A jetpropelled'airc-"raft capable of vertical take 0E t and landing crnnpgrisingl an engineI housing, three hollow 'exhaust pipes yiixedlyconnected to fsaid housing and ex-` fliiltling, therefrom' and'immovable relative thereto, the

' ends, ofssaidpipes which are remOte vfrom said housingbeing spacedapart and arranged in substantially tri angular.; formation to providestable support for said anpaft onthe ground, "'a jet-type engine mountedin housing to discharge thrust gases substantially equal-Y ly(irito'each @of saidpipes," movable valve means mountelQin eachof'sai'dpipes to selectively control .fthe quantityjofiilowdofgases'through therespective pipes toicontrol the direction of flight of' said aircraft,movable flap means adjacent the] spaced apart ends of said pipes forchanging the direction of flow of gaseskfrom ,said` pipes tt'r,co trolSihility'of the aircraft in flight, means to control the amount ofthrust produced by said engine, and manually operable control means forregulating said valve means, said ap means and said thrust control meansduring Hight of said aircraft.

5. A jet propelled aircraft comprising a main body frame consistingessentially of two portions upon which the remaining aircraft structureis mounted, said portions being a jet engine housing and a plurality ofthrust pipes fxedly and immovably connected to and depending from saidhousing, each of said thrust pipes providing support for the aircraft onthe ground whereby said aircraft is supported by all of said pipes whennot in flight, a jet engine mountedin said housing for effecting ow ofthrust gases individually through said pipes to effect propulsion ofsaid aircraft,'an lairfoil wing extending fromieach of opposite sides ofsaid housing` and fxedly and immovably mounted vrelative to both saidhousing and said pipes, valve means in each of said pipes to vary theo'wof gases'therefrom for directional control of said aircraft in flight,and ap means` adjacent the lower end of each of'said pipesfor effectingyaw control of said aircraft in flight.

6. A jet propelled aircraft comprising a main body frame consistingessentially of two. portions upon which the remaining aircraft structureis mounted, said portions being a jet engine housing and a plurality ofthrust pipes xedly and immovably connected to anddepending from saidhousing, each of said thrust pipes providing support for the aircraft onthe ground whereby said aircraft Vis supported by all of said pipes whennot in flight, a jet engine mounted in said housing for effecting flowof thrust gases individually through said'pipes to effect propulsion ofsaid aircraft, an airfoil wing extending from each of opposite sides ofsaid housing and fxedly and immovably mounted relative to both saidhousing and said pipes, valve means in each of said pipes to vary theilow of gases therefrom for directional control of said aircraft inflight, ap means adjacent the lower end of each of said pipes foreffecting yaw control of said aircraft in flight, and a pilot supportingstation rigidly connected to each of said thrust pipes and bracing thesame. Y

, 7. In an -aircraft of the type propelled solely by jet thrust gases, ajet engine housing, three thrust pipes cornmunicating with said enginehousing and extending therefrom with the ends of said pipes remote fromsaid engine housing terminating at substantially equally spacedV apartpoints, said thrust pipes depending from said engine housing andextending substantially in an upright direction when said aircraft is onthe ground, said pipe lli.

ends providing supporti forme-aircraft. on theground-,-

said engine housing being immovable relative Said thrustpipesV valvemeans mountedin each ofsaid pipes to control flow of gases throughsaidpipes to control directional ili'ght'o'f the aircraft, andrneansincluding a. universally fmounted pilot operable control memberpfQr.

controlling'selectively said valve means.

8. In a jetpropelled aircraft, ajetengine housing,` a;

plurality of` individual thrust pipescommunicating.with` said housing:and terminating in .spaced apart Sends te mote fromsaid housing, saidhousing and said thrust;- pipes` being immovable relative to each other,meansl mounted in each of said pipes to control the ow quan tity ofgasesv selectively through said pipes to control the direction ofvflightV of the aircraft, and meansV adjacent said pipe ends. to deflectthe gases owing therethrough for controlling stability of the aircraftin flight,

9,; In aiet propelledaircraft, a jet engine housing, a plurality ofindividual thrust pipes communicating with said housing and terminatingin spaced apartV ends re-A f mote from said housing, said housing andsaid thrust pipes being immovable relative to each other, means mountedin each of said pipes to control the ow quan-v tity of gases.selectively through said pipes to control the directionv of flight ofthe aircraft, means to deflect the gases` adjacent said ends ofsaidpipes -for controlling stability of the aircraft in flight, and a singlecontro column operable manually by the aircraft pilot to adjust thepositions of the flow control means and the deflecting means.

10. In a jet propelled aircraft, a jet engine housing, a

plurality of individual thrust pipes communicating with said housing andterminating in spaced apart ends spaced from said housing, said housingand said thrust pipes being immovable relative to each other, meansmounted in each of said pipes to control the ow of gases selectivelythrough said pipes to control the direction of flight of the aircraft,means to deflect the gases adjacent said ends of said pipes forcontrolling stability of the aircraft in flight, a single control columnmanually operable by the yaircraft pilot to adjustv selectively thepositions of the flow control means'and the'deecting means, means tosupply fuel toV an engine in said housing including a fuel regulatingvalve, and control means for said fuel valvepon said control column.

ing from said housing and extending substantially in an uprightdirection when the aircraft is on the ground,

said pipe ends providing support for the aircraft on the ground, a pilotsupporting station and a pilot operable control column in thev areabetween said housing and said pipe ends, a movable valve mounted in eachpipe for varying the flow quantity of gases therethrough foreectingdirectional control ofthe aircraft in flight, and means operativelyconnecting each of said valves to said control column wherebyindependent adjustment of said valves may he effected.

12. A jet propelled aircraft comprising an immovable housing for ajet-type engine, at least three individual thrustk pipes communicatingwith said housing and terminating in pipe ends spaced from said housing,said pipes depending from said housing when the aircraft is on theyground and providing support for the aircraft on the ground, a pilotsupporting station and a pilot operable control column i-n the Vareabetween said housing and said pipe ends, a movable valve mounted in eachpipe for varying the flow quantity of gases therethrough for effectingdirectional control of .the aircraft in ight, means operativelyconnecting each of said valves to said control column wherebyindependent adjustment of said valves may be effected, and adjustableilaps mounted adjacent said pipe ends in the path of the gases emanatingoperable for supporting the aircraft on 'the ground, the' upper ends ofsaid pipesfbeing connected Limmovablylzto an engine housing wherebythrust gases vproduced'in an engine in said housing flow through saidpipes 'to effect' propulsion of the aircraft, an airfoil wing extending.from each of opposite sides of said aircraft and being xedly andimmovably mounted relative to said pipes for stabilizing flight of theaircraft, valve means mounted in each of said pipes .toY vary the flowof gases therefrom for electing directional control of said aircraftin`ight, and pilot operable means for selectively controlling said valvemeans.

14. A jet propelled aircraft capable of vertical take off and landing,comprising means mounted in a housing for producing a ow of thrustgases, a plurality of individual thrust pipes connected to said housingand extending therefrom withthe ends of said pipes remote from saidhousing terminating at spaced points whereby gases produ'eea by saidmeansnaw' thrbughI-si'd'fipes to effect propulsion of the aircraft, anairfoil'wixig'f'on eachof oppositehsides of said aircraft tostabili'zeight flow of gasestherethrough for effecting.diretz'tilalcon#4 trol of the aircraftinfight'fpilot operable niean'siforselectivelyVcontrollingsaid valve means,land a pilot slipporting station comprisinga platform rigidly' connected to each of said thrust pipes and bracing.the sagrnet-y References cited in the me ofihspam" UNITED STATES PATENTSV2,486,990* Sharpe, Nov. `l, -.'l949; 2,601,104 Douglas June 17,;1952l2,622,826 Prince Dec.. 23,-,1952r 2,664,700 Benoit Ian.' 5,",19542,668,026 Price Feb; 2,-.1954 2,692,475 Hull Oct. 26, Y19544 2,693,079Rau Nov. .,2, A 1954 2,708,081 Dobson Mayvv 10, 1955 2,738,147 LeechMar. 131,"l 1956 2,774,554 Ashwood et al Dec. 18, 1956 FOREIGN PATENTS610,143 Great Britain Oct. 12, 1948 France Dec. 16,l 1953'

